US 11,808,164 B1
Simultaneously assembling rotor blades from a gas turbine engine rotor disk
Robert West, Mississauga (CA); Howard Mah, Mississauga (CA); Sowriraja Krishnasamy, Mississauga (CA); and Dean-Andrew Michalagas, Etobicoke (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Aug. 19, 2022, as Appl. No. 17/891,789.
Int. Cl. F01D 25/28 (2006.01); F01D 5/30 (2006.01)
CPC F01D 25/285 (2013.01) [F01D 5/3007 (2013.01); F05D 2230/60 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A method for assembling a rotor of a gas turbine engine, comprising:
providing a rotor disk that comprises an axis and a plurality of slots arranged circumferentially about the axis in an array;
providing a plurality of rotor blades that include a plurality of airfoils and a plurality of attachments, each of the plurality of rotor blades including a respective one of the plurality of airfoils and a respective one of the plurality of attachments;
inserting each of the plurality of attachments partially into a respective one of the plurality of slots;
resting the plurality of rotor blades on top of a blade support structure;
lowering the blade support structure axially downward along the rotor disk to simultaneously seat the plurality of attachments into the plurality of slots; and
rotating the blade support structure about the axis while the blade support structure is lowered axially downward along the rotor disk.